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GB885490A - Improvements in rocket motor assemblies - Google Patents

Improvements in rocket motor assemblies

Info

Publication number
GB885490A
GB885490A GB24463/59A GB2446359A GB885490A GB 885490 A GB885490 A GB 885490A GB 24463/59 A GB24463/59 A GB 24463/59A GB 2446359 A GB2446359 A GB 2446359A GB 885490 A GB885490 A GB 885490A
Authority
GB
United Kingdom
Prior art keywords
container
rocket motor
fuel
propellant
combustion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB24463/59A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB885490A publication Critical patent/GB885490A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • F05D2240/1281—Plug nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)

Abstract

885,490. Rocket motor assemblies. GENERAL ELECTRIC CO. July 16, 1959 [July 21, 1958], No. 24463/59. Class 110 (3). In a rocket motor assembly, the propellant container is of ring form, either circular or polygonal, and a series of rocket motor units is mounted therearound and connected thereto so as to discharge at right angles to the plane of the ring. The cross-section of the container may be round, elliptical or approximately square. In the case of mono-fuel a single fuel container is provided but where fuel and oxidizer are used two concentric containers each of ring form are provided; alternatively a single container may be partitioned to provide two compartments, The container 10 in Fig. 1 is of toroidal form and a series of rocket motor units 11 each comprising a combustion chamber, a propellant injector and a propulsion nozzle is mounted thereon, each motor discharging normally to the plane of the container 10. In Fig. 2 the combustion chambers 17 are disposed along either side of the propellant container 10 which is of square cross-section, the gases discharging along the surfaces of the guide member 18. The combustion chambers 17 may each be divided into short lengths. The fuel container 10 in Fig. 4 is partitioned to afford fuel and oxidizer chambers 22, 23 which are connected to the injectors 24 by ducts 25, 26. The combustion chambers are shown at 28 and the combustion gases discharge through the outlet nozzles along the sides of the guide plug 29. A divided combustion chamber 34 is shown in Fig. 6, the propellant injector being indicated at 33 and the dividing baffles at 36. Rocket motor assemblies may be arranged in stages. The object of the invention is to provide a rocket assembly capable of providing thrust of the order of fifty million pounds. Specification 885,489 is referred to.
GB24463/59A 1958-07-21 1959-07-16 Improvements in rocket motor assemblies Expired GB885490A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US885490XA 1958-07-21 1958-07-21

Publications (1)

Publication Number Publication Date
GB885490A true GB885490A (en) 1961-12-28

Family

ID=22212001

Family Applications (1)

Application Number Title Priority Date Filing Date
GB24463/59A Expired GB885490A (en) 1958-07-21 1959-07-16 Improvements in rocket motor assemblies

Country Status (2)

Country Link
FR (1) FR1230372A (en)
GB (1) GB885490A (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3107488A (en) * 1960-09-27 1963-10-22 Astrosyst Inc Rotating rocket motor
US3312068A (en) * 1960-12-05 1967-04-04 North American Aviation Inc Horizontal flow thrust chamber

Also Published As

Publication number Publication date
FR1230372A (en) 1960-09-15

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